eVTOL Maneuvering Reserve Display Using 4D Control Ellipsoids
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Solution Overview
Problem
Existing aircraft, particularly electric vertical take-off and landing (eVTOL) multirotor aircraft, face challenges in displaying and managing maneuvering reserves due to the complex coupling of control torques and thrust across multiple axes, making it difficult for pilots to assess and utilize the available control limits effectively.
Innovation Solution
A method and flight control device that determine a four-dimensional maneuvering reserve by approximating a control volume as a four-dimensional ellipsoid, allowing for normalization of control vectors and outputting permissible flight maneuvers, enabling intuitive display of coupled load limits and facilitating safe operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the number of propulsion units is increased to provide sufficient control authority, then the control capacity is improved, but the complexity of monitoring and managing individual unit load limits increases
Solution Approach 1:
The patent combines the monitoring of multiple individual propulsion unit load limits into a single aggregated control volume representation. Instead of displaying separate indicators for each of the 18 propulsion units, the system merges them into a unified four-dimensional control volume that represents the collective maneuvering reserve, significantly reducing monitoring complexity while maintaining complete control awareness.
Solution Approach 2:
The patent introduces a flight control device as an intermediary between the pilot and the complex propulsion system. This intermediary automatically calculates and processes the individual load limits of multiple propulsion units, transforms them into a unified control volume, and presents the information in an intuitive manner, shielding the pilot from the underlying complexity.
2Loss of information
If the control limits of individual propulsion units are displayed separately, then the load capacity information is complete, but the pilot cannot directly influence them due to the large number of units
Solution Approach 1:
The patent merges the separate control limits of multiple propulsion units into a single unified control volume that represents the aggregate maneuvering reserve. This allows the pilot to interact with one integrated control interface rather than attempting to manage 18 individual unit limits, dramatically improving ease of operation while preserving complete load capacity information through the aggregated representation.
Solution Approach 2:
The patent segments the complex control problem into two manageable parts: the flight control device automatically handles the complex calculation and aggregation of individual unit limits, while the pilot interacts with the simplified unified control volume representation. This segmentation allows each party to operate within their optimal complexity zone.
3Loss of information
If the control volume is represented in four dimensions including total thrust and control torques, then the maneuvering reserve information is comprehensive, but the display becomes difficult to visualize and use
Solution Approach 1:
The patent transforms the four-dimensional control volume information into a display format that can be perceived in two or three dimensions. By using graphical representations such as colored zones or symbolic indicators mapped to the four parameters (total thrust and three control torques), the system preserves complete maneuvering reserve information while making it visually accessible and easy to interpret for the pilot.
Data Source
AI summary
A method for determining a maneuvering reserve in an aircraft having a number of propulsion units, preferably a multirotor VTOL aircraft, most preferably an aircraft with electrically operated drive units for the rotors, including the steps: a) Determining a control vector, τ, for the aircraft, τ=(L M N F)T, the components of which represent control torques of the aircraft around the roll axis, L, the pitch axis, M, and the yaw axis, N, and a total thrust, F, b) Approximating an existing four-dimensional control volume, D, of the aircraft by a four-dimensional ellipsoid, E, the axes of which represent the control torques, L, M, N, of the aircraft and the total thrust, F, c) Determining a normalized control vector, τind=(Lind Mind Nind Find)T for the aircraft, using axis dimensions, Lmax, Mmax, Nmax, Fmax, of the ellipsoid, in particular semi-axis dimensions of the ellipsoid; and d) Outputting at least the normalized control vector, τind, for determining a permissible flight maneuver in at least one dimension of the four-dimensional control volume.